CN108884753A - Turbine wheel, radial turbine and booster - Google Patents
Turbine wheel, radial turbine and booster Download PDFInfo
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- CN108884753A CN108884753A CN201680081349.XA CN201680081349A CN108884753A CN 108884753 A CN108884753 A CN 108884753A CN 201680081349 A CN201680081349 A CN 201680081349A CN 108884753 A CN108884753 A CN 108884753A
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- Prior art keywords
- blade
- blade tip
- tip
- turbine
- radial
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
- F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
- F01D5/048—Form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of turbine wheel, radial turbine and boosters.The suction surface (46n) of the blade (42) of radial turbine has：Blade tip forequarter (47n), boundary and leading edge (43) including suction surface (46n) and blade tip (45)；And tip-side rear portion (48n), boundary and rear (44) including suction surface (46n) and blade tip (45).Blade tip forequarter (47n) is from radial, in the concave curved surface being recessed to reverse rotation side (So).Tip-side rear portion (48n) is from radial, in the convex surface to rotary side (Sr) protrusion.
Description
Technical field
The present invention relates to a kind of turbine wheel, radial turbine and boosters.
Background technique
Turbine has the whirlpool of the rotatable shaft pivoted about with axis, the peripheral side for being fixed on rotatable shaft
It takes turns impeller and covers the shell of turbine wheel.Between turbine wheel has the wheel disc for being fixed on rotatable shaft and separates in the circumferential
Every the multiple blades for the outer peripheral surface that the wheel disc is arranged in.Working fluid is from being flowed into multiple blades between the leading edge of each blade
Each other.The working fluid is flowed out between the rear of each blade.
In radial turbine, radial outside of the leading edge direction of blade relative to axis.Also, the rear of blade is towards axis
The rear side that the axis of extension upwardly extends.Therefore, in radial turbine, working fluid from radial outside flow into, side by side in the axial direction after
Side.
As such radial turbine, such as there is the radial turbine recorded in following patent document 1.The radial turbine is just
Pressure surface is in the concave curved surface being recessed to rotary side from pressure surface towards suction surface.Also, suction surface is in the convex of rotary side protrusion
Curved surface.
Conventional art document
Patent document
Patent document 1：Japanese Patent Publication 2004-011560 bulletin
Summary of the invention
The invention technical task to be solved
In turbine, in order to make turbine wheel relative rotation, the blade tip of blade and the inner peripheral surface of shell relative to shell
Between there are gaps.The gap is commonly referred to as tip clearance.In order to improve turbine efficiency, preferably reduce as far as possible between the tip
Gap.However, due to avoiding the blade tip of blade and the inner circumferential of shell using influence of shaft vibration or the thermal expansion of turbine wheel etc.
The contact in face, therefore there is limitation in the diminution of the tip clearance.
In turbine, the flowing of the working fluid by tip clearance is reduced, that is, clearance flow can promote turbine efficiency between reducing
Raising.Therefore, the purpose of the present invention is to provide a kind of turbine wheel that can reduce a clearance flow, radial turbine and pressurizations
Device.
For solving the means of technical task
As the turbine wheel of first method involved in invention for achieving the above object, have：
Wheel disc, in the shape of rotational symmetry centered on axis, before being with the axial side extended from the axis
Side towards the other side be rear side and diameter gradually decreases；And multiple blades, relative to the axis on circumferential D interval and
It is fixed on the outer peripheral surface of the wheel disc, the blade has：Leading edge, from the part of the front side of the wheel disc to including described
The direction of axial ingredient extends, and radial outside of the direction relative to the axis；Rear, from the rear side of the wheel disc
Part extends to the direction for including radial ingredient relative to the axis, and towards the rear side；Pressure surface and suction surface, from
The leading edge extends to the rear, and side opposite toward each other；Blade tip becomes the side of the side far from the outer peripheral surface
Edge, the suction surface have：And blade tip forequarter, boundary and the leading edge including the suction surface and the blade tip；And leaf
Sharp side rear portion, boundary and the rear, the blade tip forequarter including the suction surface and the blade tip are in from radial
The concave curved surface being recessed from the suction surface towards the pressure surface to reverse rotation side, the tip-side rear portion from radial,
In from the pressure surface towards the negative pressure surface side to the convex surface of rotary side protrusion.
The blade in turbine wheel blade tip and cover the turbine wheel the inner peripheral surface of turbine shroud between, there is title
For the gap of tip clearance.By the flowing of the working fluid of tip clearance, i.e., between clearance flow presence, promote under turbine efficiency
Drop.
In this, it is assumed that using suction surface generally to the blade of the convex surface of rotary side protrusion as comparative example.The comparative example
In, as clearance flow as a result, the leak fluid flowed from the pressure surface side of blade to suction surface side becomes vortex, along the blade
Suction surface flowing.Along the leak fluid of the suction surface of the blade flowing can cause it is more between clearance flow.
On the other hand, in the turbine wheel, the blade tip forequarter in the suction surface of blade is recessed to be recessed to reverse rotation side
Curved surface.Therefore, in the turbine wheel, compared to the angular distance relative to clearance flow between suction surface in comparative example, relative to negative
The angular distance of clearance flow is bigger between pressure surface.Therefore, in the turbine wheel, via between the tip in the part of the front edge side of blade
Gap, the most of leak fluid for flowing to the negative pressure surface side of the blade are not attached to the suction surface of the blade, and far from the negative pressure
Surface current is dynamic.In this way, in the turbine wheel, suction surface of most of leak fluid far from blade and flow, therefore be able to suppress
Clearance flow between initiation.As a result, can reduce a clearance flow compared to comparative example in the turbine wheel, and it can be improved turbine effect
Rate.
Turbine wheel as second method involved in invention for achieving the above object, wherein
In the turbine wheel of the first method, the suction surface has root, and the root includes and the periphery
The boundary in face, the leading edge and the rear, and be in the blade tip forequarter and the tip-side back contacts, the root
To the convex surface of the rotary side protrusion.
Turbine wheel as Third Way involved in invention for achieving the above object, wherein
In the turbine wheel of the second method, the boundary of the blade tip forequarter and root is located in blade height direction
It is upper to be less than the position that the half of blade height is not had from the blade tip.
Turbine wheel as fourth way involved in invention for achieving the above object, wherein
In described first any turbine wheel into Third Way, the blade tip forequarter and tip-side rear portion phase
Mutually contact, on the blade tip line for being formed in the boundary of the blade tip and the suction surface, the blade tip forequarter and the blade tip
The boundary at side rear portion is located at the position of more than half from the overall length that the up-front distance is the blade tip line.
Turbine wheel as the 5th mode involved in invention for achieving the above object, wherein
In any turbine wheel in first to fourth mode, the curvature of the concave curved surface of the blade tip forequarter
Radius is the radius of curvature of the convex surface at the tip-side rear portion or more.
Turbine wheel as the 6th mode involved in invention for achieving the above object, wherein
In any turbine wheel in described first to the 5th mode, the pressure surface has：Blade tip forequarter, including institute
State pressure surface and the blade tip boundary and the leading edge；And tip-side rear portion, the side including the pressure surface Yu the blade tip
Boundary and the rear, the blade tip forequarter of the pressure surface is from radial, in the evagination to the reverse rotation side protrusion
Face, the tip-side rear portion of the pressure surface is from radial, also in the concave curved surface being recessed to the rotary side.
As the radial turbine of the 7th aspect of the present invention for achieving the above object, have：
Any turbine wheel in described first to the 6th mode；Rotatable shaft, along described centered on the axis
It is axially extending, and it is fixed with the turbine wheel；And
Turbine shroud covers the turbine wheel in a rotatable way.
Booster as eighth mode involved in invention for achieving the above object, wherein
Have the radial turbine and compressor of the 7th mode, the compressor has：Compressor rotating shaft, with described
Axis pivots about；Impeller is fixed on the compressor rotating shaft；And compressor housing, the impeller is covered, it is described
Rotatable shaft and the compressor rotating shaft are located on same axis and are interconnected and rotate integrally, and become booster rotation
Axis.
Invention effect
A mode of the invention can reduce a clearance flow.
Detailed description of the invention
Fig. 1 is the cross-sectional view of the booster in an embodiment according to the present invention.
Fig. 2 is the main portion sectional view of the radial turbine in an embodiment according to the present invention.
Fig. 3 is the expanded view of the turbine wheel in an embodiment according to the present invention.
Fig. 4 is the perspective view of the turbine wheel in an embodiment according to the present invention.
Fig. 5 is the explanation of the flowing of the working fluid in the radial turbine indicated in an embodiment according to the present invention
Figure.
Fig. 6 is the explanatory diagram of the flowing of the working fluid in the radial turbine indicated in comparative example.
Specific embodiment
Below in explanation, it is illustrated using embodiment of the attached drawing to booster according to the present invention.
As shown in Figure 1, the booster of present embodiment has：Air A is compressed and is delivered to and drawn by compressor 10
It holds up；Radial turbine 30 is driven by its body of the discharge from engine EX；And linking part 20, connection compressor 10 and radial whirlpool
Wheel 30.
Compressor 10 has：Compressor rotating shaft 11 is pivoted about with axis Ar and is cylindric；Compressor leaf
Wheel 16, is installed on the periphery of compressor rotating shaft 11；And compressor housing 12, cover compressor impeller 16.
Radial turbine 30 has：Rotatable shaft 31 is pivoted about with axis Ar；Turbine wheel 40, is installed on
Rotatable shaft 31；And turbine shroud 32, cover turbine wheel 40.
Linking part 20 has：Link rotary shaft 21, pivoted about with axis Ar, and is cylindric；Center housing
22, covering connection rotary shaft 21；And bearing 23, bearing links rotary shaft 21 in a rotatable way.Bearing 23 is fixed on center
The inner circumferential side of shell 22.
Be configured in order on same axis Ar compressor rotating shaft 11 axis Ar, link rotary shaft 21 axis Ar and
The axis Ar of rotatable shaft 31.Compressor rotating shaft 11, connection rotary shaft 21 and rotatable shaft 31 are interconnected and integrated
Rotation, and become booster rotary shaft.Also, compressor housing 12, center housing 22 and turbine shroud 32 are interconnected to be formed
For pressurizer shell.
Here, the extending direction of axis Ar is set as axial Da, the side of axial direction Da is set as axial front side Daf, is somebody's turn to do
The other side of axial Da is set as axial rear side Dab.In present embodiment, relative to linking part 20, compressor 10 is set to axial direction
Front side Daf, radial turbine 30 are set to axial rear side Dab relative to linking part 20.Also, by the radial direction relative to axis Ar
Referred to as radial direction Dr will be set as radial outside Dro far from the side of axis Ar on radial Dr, by radial Dr close to axis Ar's
Side is set as radially inner side Dri.Also, the circumferential direction centered on axis Ar is referred to as circumferential direction Dc.And by circumferential direction Dc, turbine
The side that impeller 40 is rotated is set as the side Dcr that rotates in a circumferential direction.
As shown in Figure 2 to 4, turbine wheel 40 has wheel disc 41 and multiple blades 42.Wheel disc 41, which is in axis Ar, is
The shape of heart rotational symmetry, and diameter is gradually reduced with towards axial rear side Dab.Between multiple blades 42 separate on circumferential Dc
Every the outer peripheral surface 41a for being fixed on wheel disc 41.
As shown in Figures 2 and 4, blade 42 has leading edge 43, rear 44, blade tip 45, pressure surface 46p and suction surface 46n.Before
Edge 43 extends from the part of the axial front side Daf of wheel disc 41 to the direction for including axial ingredient, and towards radial outside Dro.Afterwards
Edge 44 extends from the part of the axial rear side Dab of wheel disc 41 to the direction for including radial ingredient, and towards axial rear side Dab.Just
Pressure surface 46p and suction surface 46n extends to rear 44 from leading edge 43, and towards mutually opposite side.Therefore, pressure surface 46p and
Suction surface 46n be back to relationship.Suction surface 46n is towards the side Dcr that rotates in a circumferential direction, and pressure surface 46p is towards opposite to that side.
Blade tip 45 is the edge of the separate side the outer peripheral surface 41a of the slave wheel disc 41 of blade 42.
Suction surface 46n has：Blade tip forequarter 47n, tip-side rear portion 48n and root 49n.Blade tip forequarter 47n is packet
Include the boundary of blade tip 45 and suction surface 46n and the part of leading edge 43.Tip-side rear portion 48n is to contact simultaneously with blade tip forequarter 47n
The part on boundary and rear 44 including blade tip 45 and suction surface 46n.Root 49n is, after blade tip forequarter 47n and tip-side
The part on the boundary of portion 48n contact and the outer peripheral surface 41a including wheel disc 41 and suction surface 46n, leading edge 43 and rear 44.Suction surface
The part that blade tip forequarter 47n, tip-side rear portion 48n and root 49n in 46n do not overlap.
Here, by rotary side Sr is set as from pressure surface 46p towards the side of suction surface 46n (with reference to Fig. 3).Also, it will be from
The side of suction surface 46n towards pressure surface 46p are set as reverse rotation side So.
As shown in figure 3, blade tip forequarter 47n from the radial direction relative to the blade 42, is recessed in reverse rotation side So
Concave curved surface.Tip-side rear portion 48n is from the radial direction relative to the blade 42, in the convex surface to rotary side Sr protrusion.It is negative
The root 49n of pressure surface 46n is from the radial direction relative to the blade 42, in the convex surface to rotary side Sr protrusion.
The radius of curvature R 1 of concave curved surface in blade tip forequarter 47n, the song of the convex surface in for example, tip-side rear portion 48n
Rate radius R2 or more.Also, on the blade tip line 45l that the boundary of blade tip 45 and suction surface 46n are formed, blade tip forequarter 47n and
The boundary b of tip-side rear portion 48n, such as positioned at the position of more than half from the overall length that the distance of leading edge 43 is blade tip line 45l.
Also, as shown in Fig. 2, the boundary of blade tip forequarter 47n and root 49n are located on blade height direction from blade tip 45 to being less than
The position of the half of blade height.
As shown in Figures 2 and 4, after pressure surface 46p also has blade tip forequarter 47p, tip-side identically as suction surface 46n
Portion 48p and root 49p.Blade tip forequarter 47p is the boundary and the part of leading edge 43 for including blade tip 45 and pressure surface 46p.Blade tip
Side rear portion 48p is to contact with blade tip forequarter 47p, and the boundary including blade tip 45 and pressure surface 46p and the part of rear 44.
Root 49p is to contact with blade tip forequarter 47p and tip-side rear portion 48p, and outer peripheral surface 41a and pressure surface including wheel disc 41
The part on the boundary of 46p, leading edge 43 and rear 44.Blade tip forequarter 47p, tip-side rear portion 48p and root in pressure surface 46p
The part that 49p does not overlap.
As shown in figure 3, the blade tip forequarter 47p of pressure surface 46p from the radial direction relative to the blade 42, is in half
The convex surface of rotary side So protrusion.The tip-side rear portion 48p of pressure surface 46p is also in from radial relative to the blade 42
The concave curved surface being recessed to rotary side Sr.In addition, the root 49p of pressure surface 46p is also in from the radial direction relative to the blade 42
The concave curved surface being recessed to rotary side Sr.
As shown in Figure 1, being formed with the blade wheel chamber that can accommodate turbine wheel 40 in a rotatable way in turbine shroud 32
33, the outlet 35 for rolling flow path 34 and working fluid F being discharged of working fluid F (EX) is flowed into.Rolling flow path 34 is to including
The flow path that the direction of circumferential ingredient extends.The part for the axial rear side Dab that flow path 34 is blade wheel chamber 33 is rolled, and in blade wheel chamber 33
The part of radial outside Dro be connected to blade wheel chamber 33.The working fluid F for rolling flow path 34 is flowed into via the connected component,
It is flowed into blade wheel chamber 33 from radial outside Dro.Blade wheel chamber 33 on rear side of axial direction Dab it is open-ended.The opening is above-mentioned
Outlet 35.The working fluid F for flowing into blade wheel chamber 33 is discharged from the outlet 35.
As shown in figure 5, flow into the working fluid F of blade wheel chamber 33 from the leading edge 43 of each blade 42 in turbine wheel 40 it
Between flow into blade 42 between.The working fluid F flowed between blade 42 is flowed out between the rear 44 of each blade 42.Workflow
During body F flows between blade 42, rotary force is assigned to turbine wheel 40.In addition, in present embodiment, working fluid
F is discharge gas EX.
Between the blade tip 45 of blade 42 and the opposite part of the inner peripheral surface of turbine shroud 32 and blade tip 45, there is referred to as tip
The gap of clearance C t (referring to Fig. 2).In order to improve turbine efficiency, tip clearance Ct is preferably minimized.However, in order to avoid
Because of shaft vibration or the influence of the thermal expansion of turbine wheel 40 etc., and the inner circumferential face contact of the blade tip 45 of blade 42 and turbine shroud 32
Risk, because reduce tip clearance Ct exist limitation.
It can promote the decline of turbine efficiency by the presence of clearance flow between the flowing i.e. of the working fluid F of tip clearance Ct.Cause
This, it is expected that clearance flow between reducing.
Here, before being illustrated to the gap stream in present embodiment, with reference to Fig. 6 in the turbine wheel of comparative example
Gap stream is illustrated.
The turbine wheel 40c of comparative example also has wheel disc 41c and multiple blade 42c.The pressure surface 46pc's of blade 42c is whole
Body is in the concave curved surface being recessed to rotary side Sr.Also, the entirety of the suction surface 46nc of blade 42c is in rotary side Sr protrusion
Convex surface.
It has been observed that flowing into most of work between the first blade 42cx and the second blade 42cy adjacent on circumferential Dc
Fluid F is flowed out between the rear 44 of these blades 42cx, 42cy.However, the working fluid F of a part is from the second blade 42cy
The side pressure surface 46pc via the tip clearance Ct in second blade 42cy, as leak fluid Fl to second blade 42cy
The side suction surface 46nc flowing.That is, the working fluid F of a part is via the tip clearance Ct in the second blade 42cy, as letting out
Leakage current body Fl is flowed between the second blade 42cy and third blade 42cz.
The leak fluid Fl flowed between the second blade 42cy and third blade 42cz becomes vortex, is attached to the second blade
The suction surface 46nc of 42cy, and flowed along suction surface 46nc.According to the leakage of the suction surface 46nc along second blade 42cy
The flowing of fluid Fl can cause a clearance flow.Therefore, according to clearance flow between the generation of the part of 43 side of leading edge of the second blade 42cy
Fc can also generate a clearance flow in the leading edge 43 of the second blade 42cy and the middle section of rear 44.Pass through the gap caused
Stream, the leak fluid Fl flowed between the second blade 42cy and third blade 42cz also becomes vortex, along the second blade 42cy
Suction surface 46nc flowing.According to the flowing of the leak fluid Fl of the suction surface 46nc along second blade 42cy, can also cause
Between clearance flow.Therefore, by the clearance flow between the middle section of the second blade 42cy generates, in the rear 44 1 of the second blade 42cy
The part of side can also generate a clearance flow.
That is, in a comparative example, from the leading edge 43 of blade 42c generated into the blade 42c entirety of rear 44 between clearance flow.
Then, the gap stream in present embodiment is illustrated with reference to Fig. 5.
In present embodiment, a part of the working fluid F flowed between the first blade 42x and the second blade 42y also can
In the part of 43 side of leading edge of the second blade 42y, as leak fluid Fl, passed through from the side pressure surface 46p of the second blade 42y
By the tip clearance Ct in second blade 42y, the side suction surface 46n of second blade 42y is flowed into.That is, the work of a part
Make fluid F as leak fluid Fl, via the tip clearance Ct in the part of 43 side of leading edge of the second blade 42y, flows into the
Between two blade 42y and third blade 42z.
The leak fluid Fl flowed between the second blade 42y and third blade 42z also becomes vortex in the present embodiment.
But in the present embodiment, most of leak fluid Fl leaves the suction surface 46n of the second blade 42y, to second blade
(as 44 side of rear of these blades 42y, 42z) is flowed between 42y and third blade 42z.
The suction surface 46nc of comparative example is generally to the convex surface of rotary side Sr protrusion.On the other hand, present embodiment
Blade tip forequarter 47n in suction surface 46n is the concave curved surface being recessed to reverse rotation side So.Therefore, compared to the phase in comparative example
For the angular distance alpha 2 of clearance flow Fc between suction surface 46nc, in present embodiment relative to clearance flow Fc between suction surface 46n
Angular distance alpha 1 is bigger.In addition angular distance alpha be tangent line and clearance flow Fc angulation between this, the tangent line be between clearance flow Fc relative to
The tangent line of suction surface in the position on the boundary of suction surface and blade tip.Therefore, in present embodiment, via the second blade
Tip clearance Ct in the part of 43 side of leading edge of 42y, flows into the big portion between the second blade 42y and third blade 42z
Point leak fluid Fl is not attached to the suction surface 46n of the second blade 42y and leaves suction surface 46n flowing.Leak fluid Fl
Flowing the suction surface 46n of the second blade 42y between, flow between the second blade 42y and third blade 42z
Working fluid F.
As a result, in present embodiment, even if producing a clearance flow in the part of 43 side of leading edge of the second blade 42y
Fc, clearance flow Fc between will not causing because of this clearance flow Fc newly.It therefore, can be more compared to comparative example in present embodiment
Clearance flow Fc between reduction improves turbine efficiency.
However, substantially tip clearance Ct can also become smaller if the size of radial turbine 30 becomes smaller.However, even if radial
The size of turbine 30 becomes smaller, and tip clearance Ct will not become so small.Its reason it has been observed that be because tip clearance Ct be for
Avoid the inner circumferential of due tos shaft vibration or the influence of the thermal expansion of turbine wheel 40 etc. the blade tip 45 of blade 42 and turbine shroud 32
The gap of face contact.It is radial accordingly, with respect to the ratio of the tip clearance Ct of the length of length or rear 44 relative to leading edge 43
Turbine 30 becomes bigger more minimizing.Therefore, radial turbine 30 more minimizes, relative to the workflow for flowing into radial turbine 30
The flow of body F, the ratio of the flow of clearance flow become higher.
Thus, for example in the radial turbine 30 of medium-sized or pony car booster, in order to improve a clearance flow
Low Minus rate, it has been observed that the side on blade tip line 45l, between the blade tip forequarter 47n in suction surface 46n and tip-side rear portion 48n
Boundary b is preferably in the position of more than half from the overall length that the distance of leading edge 43 is blade tip line 45l.Also, it has been observed that before tip-side
The radius of curvature R 1 of concave curved surface in portion 47n is preferably 2 or more the radius of curvature R of the convex surface in the 48n of tip-side rear portion.
Industrial availability
A mode of the invention can reduce a clearance flow.
Symbol description
10- compressor, 11- compressor rotating shaft, 12- compressor housing, 16- compressor impeller, 20- linking part, 21- connect
Knot rotary shaft, 22- center housing, 23- bearing, 30- radial turbine, 31- rotatable shaft, 32- turbine shroud, 33- blade wheel chamber,
34- rolling flow path, 35- outlet, 40- turbine wheel, 41- wheel disc, 41a- outer peripheral surface, 42- blade, 43- leading edge, 44- rear,
45- blade tip, 45l- blade tip line, 46n- suction surface, 46p- pressure surface, 47n, 47p- blade tip forequarter, after 48n, 48p- tip-side
Portion, the root 49n, 49p-, Ct- tip clearance, F- working fluid, clearance flow between Fc-, Fl- leak fluid, Ar- axis, Da- is axial,
The axial rear side of Dab-, Daf- axial front side, Dc- is circumferential, and Dr- is radial, Dri- radially inner side, Dro- radial outside, Sr- rotation
Side, So- reverse rotation side.
Claims (8)
1. a kind of turbine wheel, has：
Wheel disc, in the shape of rotational symmetry centered on axis, as the axial side extended from the axis is front side
It is that rear side diameter is gradually reduced towards the other side；And
Multiple blades, relative to the axis on circumferential D interval and be fixed on the outer peripheral surface of the wheel disc,
The blade has：
Leading edge extends from the part of the front side of the wheel disc along the direction for including the axial ingredient, and towards relative to
The radial outside of the axis；
Rear, the part edge from the rear side of the wheel disc include that the direction of the radial ingredient relative to the axis extends,
And towards the rear side；
Pressure surface and suction surface extend to the rear from the leading edge, and opposite side toward each other；And
Blade tip becomes the edge of the side far from the outer peripheral surface,
The suction surface has：Blade tip forequarter, boundary and the leading edge including the suction surface and the blade tip；And blade tip
Side rear portion, boundary and the rear including the suction surface and the blade tip,
The blade tip forequarter is from radial, in recessed from the suction surface towards being recessed to reverse rotation side for the pressure surface
Curved surface,
The tip-side rear portion from radial, in from the pressure surface towards the negative pressure surface side to the convex of rotary side protrusion
Curved surface.
2. turbine wheel according to claim 1, wherein
The suction surface have root, the root include with the boundary of the outer peripheral surface, the leading edge and the rear, and with
The blade tip forequarter and the tip-side back contacts,
The root is in the convex surface to the rotary side protrusion.
3. turbine wheel according to claim 2, wherein
The boundary of the blade tip forequarter and root, which is located at, to be less than on blade height direction from the blade tip to blade height
The position of half.
4. according to claim 1 to 3 described in any item turbine wheels, wherein
The blade tip forequarter and the tip-side rear portion contact with each other,
On the blade tip line for being formed in the boundary of the blade tip and the suction surface, after the blade tip forequarter and the tip-side
The boundary in portion is located at the position of more than half from the overall length that the up-front distance is the blade tip line.
5. described in any item turbine wheels according to claims 1 to 4, wherein
The radius of curvature of the concave curved surface in the blade tip forequarter is the song of the convex surface in the tip-side rear portion
It is more than rate radius.
6. according to claim 1 to 5 described in any item turbine wheels, wherein
The pressure surface has：Blade tip forequarter, boundary and the leading edge including the pressure surface and the blade tip；And blade tip
Side rear portion, boundary and the rear including the pressure surface and the blade tip,
The blade tip forequarter of the pressure surface is in radial observation, in the convex surface to the reverse rotation side protrusion,
The tip-side rear portion of the pressure surface is in radial observation, also in the concave curved surface being recessed to the rotary side.
7. a kind of radial turbine, has：
Described in any item turbine wheels of claim 1 to 6；
Rotatable shaft to described axially extending centered on the axis, and is fixed with the turbine wheel；And
Turbine shroud covers the turbine wheel in a rotatable way.
8. a kind of booster, has：
Radial turbine described in claim 7；And
Compressor,
The compressor has：
Compressor rotating shaft is pivoted about with the axis；
Impeller is fixed on the compressor rotating shaft；And
Compressor housing covers the impeller,
The rotatable shaft and the compressor rotating shaft are located on same axis and are interconnected and rotate integrally, and become increasing
Depressor rotary shaft.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/JP2016/056381 WO2017149693A1 (en) | 2016-03-02 | 2016-03-02 | Turbine wheel, radial turbine, and supercharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108884753A true CN108884753A (en) | 2018-11-23 |
| CN108884753B CN108884753B (en) | 2021-07-06 |
Family
ID=59743648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680081349.XA Active CN108884753B (en) | 2016-03-02 | 2016-03-02 | Turbine wheel, radial turbine and supercharger |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10746025B2 (en) |
| EP (1) | EP3401525B1 (en) |
| JP (1) | JP6583946B2 (en) |
| CN (1) | CN108884753B (en) |
| WO (1) | WO2017149693A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116044514A (en) * | 2023-03-17 | 2023-05-02 | 潍柴动力股份有限公司 | Turbine and turbocharger |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20180134965A (en) * | 2016-04-25 | 2018-12-19 | 보르그워너 인코퍼레이티드 | Turbine wheel for turbines |
| DE102020114387A1 (en) * | 2020-05-28 | 2021-12-02 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Fan wheel with three-dimensionally curved impeller blades |
| US11867078B2 (en) * | 2022-06-11 | 2024-01-09 | Garrett Transportation I Inc. | Turbine wheel |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1737378A (en) * | 2004-08-20 | 2006-02-22 | 三星Techwin株式会社 | Radial-flow turbine wheel |
| JP2008133766A (en) * | 2006-11-28 | 2008-06-12 | Ihi Corp | Turbine impeller |
| CN101341312A (en) * | 2006-11-20 | 2009-01-07 | 三菱重工业株式会社 | Diagonal flow turbine, or radial turbine |
| CN102459818A (en) * | 2009-06-26 | 2012-05-16 | 三菱重工业株式会社 | Turbine rotor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3836050B2 (en) | 2002-06-07 | 2006-10-18 | 三菱重工業株式会社 | Turbine blade |
-
2016
- 2016-03-02 JP JP2018502937A patent/JP6583946B2/en active Active
- 2016-03-02 US US16/075,779 patent/US10746025B2/en active Active
- 2016-03-02 CN CN201680081349.XA patent/CN108884753B/en active Active
- 2016-03-02 WO PCT/JP2016/056381 patent/WO2017149693A1/en active Application Filing
- 2016-03-02 EP EP16892535.2A patent/EP3401525B1/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1737378A (en) * | 2004-08-20 | 2006-02-22 | 三星Techwin株式会社 | Radial-flow turbine wheel |
| CN101341312A (en) * | 2006-11-20 | 2009-01-07 | 三菱重工业株式会社 | Diagonal flow turbine, or radial turbine |
| JP2008133766A (en) * | 2006-11-28 | 2008-06-12 | Ihi Corp | Turbine impeller |
| CN102459818A (en) * | 2009-06-26 | 2012-05-16 | 三菱重工业株式会社 | Turbine rotor |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116044514A (en) * | 2023-03-17 | 2023-05-02 | 潍柴动力股份有限公司 | Turbine and turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| JPWO2017149693A1 (en) | 2018-11-22 |
| JP6583946B2 (en) | 2019-10-02 |
| US10746025B2 (en) | 2020-08-18 |
| EP3401525A1 (en) | 2018-11-14 |
| EP3401525B1 (en) | 2020-09-16 |
| US20190040743A1 (en) | 2019-02-07 |
| WO2017149693A1 (en) | 2017-09-08 |
| EP3401525A4 (en) | 2019-01-02 |
| CN108884753B (en) | 2021-07-06 |
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